NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.89 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls421-il-1000000.txt Download as CSV file: xf-ls421-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0906 0.08018 0.07589 -0.0722 1.0000 0.0238
-19.500 -1.0931 0.07641 0.07204 -0.0739 1.0000 0.0239
-19.250 -1.0939 0.07291 0.06846 -0.0754 1.0000 0.0241
-19.000 -1.0935 0.06958 0.06505 -0.0768 1.0000 0.0242
-18.750 -1.0920 0.06640 0.06180 -0.0782 1.0000 0.0244
-18.500 -1.0894 0.06341 0.05874 -0.0794 1.0000 0.0245
-18.250 -1.0925 0.05989 0.05515 -0.0807 1.0000 0.0247
-18.000 -1.0949 0.05649 0.05170 -0.0818 1.0000 0.0250
-17.750 -1.0935 0.05357 0.04873 -0.0828 1.0000 0.0252
-17.500 -1.0880 0.05096 0.04607 -0.0842 0.9793 0.0255
-17.250 -1.0832 0.04873 0.04375 -0.0845 0.9545 0.0258
-17.000 -1.0779 0.04686 0.04179 -0.0842 0.9374 0.0261
-16.750 -1.0717 0.04499 0.03982 -0.0841 0.9248 0.0264
-16.500 -1.0632 0.04331 0.03805 -0.0840 0.9143 0.0267
-16.250 -1.0546 0.04161 0.03627 -0.0840 0.9054 0.0270
-16.000 -1.0438 0.04011 0.03469 -0.0840 0.8972 0.0274
-15.750 -1.0331 0.03864 0.03312 -0.0839 0.8891 0.0277
-15.500 -1.0203 0.03730 0.03171 -0.0840 0.8834 0.0280
-15.250 -1.0123 0.03562 0.02997 -0.0838 0.8770 0.0283
-15.000 -1.0057 0.03389 0.02816 -0.0835 0.8706 0.0288
-14.750 -0.9945 0.03253 0.02676 -0.0834 0.8654 0.0293
-14.500 -0.9816 0.03131 0.02551 -0.0832 0.8606 0.0297
-14.250 -0.9673 0.03028 0.02443 -0.0830 0.8556 0.0302
-14.000 -0.9529 0.02926 0.02335 -0.0827 0.8505 0.0307
-13.750 -0.9376 0.02832 0.02234 -0.0825 0.8454 0.0313
-13.500 -0.9206 0.02746 0.02145 -0.0824 0.8418 0.0317
-13.250 -0.9068 0.02640 0.02034 -0.0821 0.8375 0.0322
-13.000 -0.8946 0.02525 0.01915 -0.0816 0.8332 0.0330
-12.750 -0.8786 0.02438 0.01825 -0.0812 0.8288 0.0336
-12.500 -0.8614 0.02361 0.01742 -0.0810 0.8243 0.0343
-12.250 -0.8430 0.02287 0.01667 -0.0808 0.8217 0.0350
-12.000 -0.8238 0.02220 0.01596 -0.0807 0.8186 0.0357
-11.750 -0.8056 0.02146 0.01519 -0.0804 0.8153 0.0363
-11.500 -0.7903 0.02055 0.01426 -0.0799 0.8118 0.0373
-11.250 -0.7718 0.01986 0.01355 -0.0796 0.8083 0.0382
-11.000 -0.7521 0.01927 0.01291 -0.0794 0.8039 0.0391
-10.750 -0.7313 0.01872 0.01234 -0.0793 0.8014 0.0401
-10.500 -0.7119 0.01807 0.01167 -0.0790 0.7988 0.0411
-10.250 -0.6937 0.01736 0.01096 -0.0786 0.7960 0.0424
-10.000 -0.6739 0.01680 0.01040 -0.0782 0.7932 0.0436
-9.750 -0.6561 0.01633 0.00989 -0.0774 0.7902 0.0447
-9.500 -0.6363 0.01582 0.00935 -0.0770 0.7873 0.0460
-9.250 -0.6140 0.01530 0.00882 -0.0772 0.7838 0.0477
-9.000 -0.5892 0.01487 0.00838 -0.0776 0.7812 0.0496
-8.750 -0.5638 0.01439 0.00791 -0.0782 0.7794 0.0518
-8.500 -0.5373 0.01394 0.00748 -0.0789 0.7772 0.0548
-8.250 -0.5103 0.01351 0.00707 -0.0797 0.7748 0.0589
-8.000 -0.4829 0.01310 0.00670 -0.0804 0.7724 0.0646
-7.750 -0.4553 0.01271 0.00635 -0.0811 0.7702 0.0731
-7.500 -0.4273 0.01232 0.00601 -0.0818 0.7679 0.0840
-7.250 -0.3988 0.01195 0.00571 -0.0826 0.7655 0.0969
-7.000 -0.3698 0.01163 0.00544 -0.0835 0.7627 0.1113
-6.750 -0.3403 0.01129 0.00518 -0.0845 0.7603 0.1284
-6.500 -0.3102 0.01092 0.00492 -0.0856 0.7589 0.1473
-6.250 -0.2797 0.01055 0.00467 -0.0867 0.7571 0.1698
-6.000 -0.2487 0.01015 0.00441 -0.0880 0.7551 0.1977
-5.750 -0.2171 0.00973 0.00415 -0.0895 0.7531 0.2330
-5.500 -0.1848 0.00932 0.00391 -0.0910 0.7512 0.2734
-5.250 -0.1522 0.00895 0.00370 -0.0926 0.7493 0.3118
-5.000 -0.1190 0.00861 0.00350 -0.0943 0.7474 0.3510
-4.750 -0.0854 0.00827 0.00331 -0.0960 0.7453 0.3926
-4.500 -0.0514 0.00796 0.00315 -0.0978 0.7428 0.4374
-4.250 -0.0166 0.00764 0.00302 -0.0998 0.7400 0.4916
-4.000 0.0177 0.00739 0.00295 -0.1015 0.7388 0.5408
-3.750 0.0508 0.00730 0.00295 -0.1027 0.7374 0.5699
-3.500 0.0832 0.00728 0.00296 -0.1037 0.7356 0.5860
-3.250 0.1155 0.00729 0.00296 -0.1047 0.7336 0.5986
-3.000 0.1475 0.00729 0.00300 -0.1055 0.7316 0.6084
-2.750 0.1796 0.00733 0.00301 -0.1064 0.7295 0.6166
-2.500 0.2113 0.00734 0.00303 -0.1072 0.7274 0.6235
-2.250 0.2429 0.00739 0.00308 -0.1080 0.7251 0.6294
-2.000 0.2747 0.00748 0.00312 -0.1088 0.7224 0.6346
-1.750 0.3065 0.00757 0.00318 -0.1096 0.7193 0.6394
-1.500 0.3376 0.00756 0.00322 -0.1103 0.7170 0.6452
-1.250 0.3690 0.00757 0.00324 -0.1110 0.7139 0.6488
-1.000 0.4004 0.00757 0.00323 -0.1117 0.7103 0.6518
-0.750 0.4318 0.00757 0.00321 -0.1124 0.7061 0.6545
-0.500 0.4631 0.00763 0.00321 -0.1131 0.7013 0.6567
-0.250 0.4946 0.00767 0.00323 -0.1139 0.6980 0.6585
0.000 0.5259 0.00761 0.00320 -0.1147 0.6948 0.6615
0.250 0.5568 0.00759 0.00320 -0.1153 0.6902 0.6642
0.500 0.5874 0.00761 0.00320 -0.1158 0.6840 0.6670
0.750 0.6179 0.00768 0.00326 -0.1163 0.6784 0.6705
1.000 0.6488 0.00771 0.00332 -0.1170 0.6738 0.6737
1.250 0.6797 0.00774 0.00334 -0.1176 0.6683 0.6759
1.500 0.7102 0.00781 0.00336 -0.1182 0.6623 0.6778
1.750 0.7412 0.00785 0.00341 -0.1189 0.6569 0.6793
2.000 0.7719 0.00784 0.00340 -0.1195 0.6497 0.6815
2.250 0.8016 0.00788 0.00341 -0.1200 0.6414 0.6838
2.500 0.8320 0.00789 0.00345 -0.1206 0.6327 0.6857
2.750 0.8611 0.00798 0.00351 -0.1209 0.6217 0.6875
3.000 0.8905 0.00807 0.00358 -0.1213 0.6077 0.6891
3.250 0.9186 0.00821 0.00366 -0.1214 0.5892 0.6907
3.500 0.9449 0.00845 0.00380 -0.1212 0.5644 0.6923
3.750 0.9685 0.00884 0.00402 -0.1206 0.5281 0.6939
4.000 0.9894 0.00936 0.00433 -0.1195 0.4862 0.6957
4.250 1.0090 0.00993 0.00469 -0.1182 0.4454 0.6974
4.500 1.0278 0.01049 0.00506 -0.1167 0.4092 0.6988
4.750 1.0462 0.01103 0.00543 -0.1152 0.3755 0.7000
5.000 1.0630 0.01158 0.00582 -0.1134 0.3456 0.7010
5.250 1.0788 0.01206 0.00619 -0.1115 0.3189 0.7032
5.500 1.0896 0.01255 0.00658 -0.1085 0.2970 0.7055
5.750 1.0996 0.01313 0.00707 -0.1055 0.2768 0.7075
6.000 1.1136 0.01378 0.00764 -0.1034 0.2571 0.7095
6.250 1.1283 0.01445 0.00823 -0.1015 0.2393 0.7114
6.500 1.1435 0.01513 0.00884 -0.0998 0.2228 0.7133
6.750 1.1589 0.01584 0.00947 -0.0982 0.2075 0.7151
7.000 1.1746 0.01655 0.01012 -0.0968 0.1941 0.7168
7.250 1.1905 0.01728 0.01080 -0.0954 0.1822 0.7185
7.500 1.2060 0.01806 0.01152 -0.0940 0.1715 0.7201
7.750 1.2230 0.01876 0.01218 -0.0928 0.1630 0.7215
8.000 1.2395 0.01951 0.01290 -0.0917 0.1554 0.7226
8.250 1.2566 0.02023 0.01359 -0.0906 0.1486 0.7250
8.500 1.2734 0.02097 0.01434 -0.0896 0.1424 0.7275
8.750 1.2902 0.02172 0.01508 -0.0885 0.1368 0.7297
9.000 1.3060 0.02254 0.01590 -0.0874 0.1315 0.7319
9.250 1.3230 0.02330 0.01666 -0.0864 0.1273 0.7341
9.500 1.3383 0.02417 0.01751 -0.0853 0.1226 0.7362
9.750 1.3549 0.02498 0.01833 -0.0844 0.1191 0.7383
10.000 1.3710 0.02582 0.01918 -0.0834 0.1156 0.7402
10.250 1.3853 0.02678 0.02011 -0.0822 0.1116 0.7420
10.500 1.4014 0.02764 0.02099 -0.0813 0.1088 0.7436
10.750 1.4169 0.02854 0.02190 -0.0803 0.1060 0.7452
11.000 1.4314 0.02950 0.02288 -0.0793 0.1030 0.7482
11.250 1.4455 0.03053 0.02393 -0.0783 0.1004 0.7508
11.500 1.4611 0.03145 0.02489 -0.0775 0.0983 0.7532
11.750 1.4756 0.03246 0.02592 -0.0765 0.0959 0.7555
12.000 1.4881 0.03364 0.02710 -0.0754 0.0932 0.7577
12.250 1.5018 0.03476 0.02825 -0.0745 0.0912 0.7601
12.500 1.5168 0.03578 0.02931 -0.0737 0.0894 0.7623
12.750 1.5305 0.03692 0.03046 -0.0729 0.0874 0.7644
13.000 1.5414 0.03829 0.03183 -0.0718 0.0853 0.7664
13.250 1.5534 0.03959 0.03317 -0.0709 0.0834 0.7699
13.500 1.5682 0.04066 0.03430 -0.0703 0.0819 0.7728
13.750 1.5802 0.04200 0.03568 -0.0694 0.0801 0.7754
14.000 1.5910 0.04345 0.03714 -0.0685 0.0783 0.7780
14.250 1.5994 0.04510 0.03881 -0.0675 0.0763 0.7805
14.500 1.6124 0.04641 0.04018 -0.0669 0.0752 0.7831
14.750 1.6240 0.04782 0.04163 -0.0662 0.0738 0.7853
15.000 1.6349 0.04931 0.04315 -0.0655 0.0723 0.7878
15.250 1.6430 0.05110 0.04497 -0.0647 0.0707 0.7911
15.500 1.6493 0.05305 0.04697 -0.0638 0.0692 0.7940
15.750 1.6614 0.05449 0.04847 -0.0633 0.0681 0.7970
16.000 1.6703 0.05625 0.05029 -0.0627 0.0669 0.8000
16.250 1.6785 0.05808 0.05215 -0.0621 0.0657 0.8030
16.500 1.6851 0.06008 0.05418 -0.0615 0.0644 0.8055
16.750 1.6872 0.06260 0.05674 -0.0608 0.0630 0.8087
17.000 1.6962 0.06440 0.05862 -0.0603 0.0622 0.8121
17.250 1.7031 0.06646 0.06076 -0.0599 0.0613 0.8153
17.500 1.7097 0.06857 0.06293 -0.0596 0.0602 0.8185
17.750 1.7141 0.07093 0.06533 -0.0592 0.0592 0.8215
18.000 1.7164 0.07355 0.06799 -0.0589 0.0582 0.8243
18.250 1.7149 0.07664 0.07113 -0.0585 0.0572 0.8272
18.500 1.7183 0.07918 0.07377 -0.0584 0.0565 0.8307
18.750 1.7225 0.08168 0.07636 -0.0583 0.0558 0.8342
19.000 1.7260 0.08427 0.07902 -0.0583 0.0550 0.8377
19.250 1.7272 0.08716 0.08198 -0.0584 0.0542 0.8410
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)